FIELD: engines and pumps.
SUBSTANCE: proposed system of gas turbine engine comprises radial-flow compressor feeding combustion chamber via diffuser, inner casing with, in fact, L-shape cross-section attached to said diffuser to extend along the flow to turbine vent air injection means, and annular sheet element of convection. The latter is arranged in radial direction between combustion chamber and said inner casing to extend axially from said diffuser to said injection means along radially inner wall of combustion chamber to constrict, together with chamber inner wall, the annular air flow channel without airflow separation and with reduced loss in head. Annular channel serves to feed aforesaid openings made in combustion chamber inner wall and air injection means.
EFFECT: higher efficiency.
9 cl, 3 dwg
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